CN112577070B - Low-resistance and high-efficiency scramjet engine thrust chamber integrated design method - Google Patents

Low-resistance and high-efficiency scramjet engine thrust chamber integrated design method Download PDF

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CN112577070B
CN112577070B CN202011406621.1A CN202011406621A CN112577070B CN 112577070 B CN112577070 B CN 112577070B CN 202011406621 A CN202011406621 A CN 202011406621A CN 112577070 B CN112577070 B CN 112577070B
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wall surface
molded line
compression section
compression
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CN112577070A (en
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孙明波
王前程
杨揖心
蔡尊
赵国焱
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National University of Defense Technology
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/14—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines with external combustion, e.g. scram-jet engines
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/17—Mechanical parametric or variational design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation

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Abstract

The invention discloses a low-resistance and high-efficiency scramjet engine thrust chamber integrated design method.A thrust chamber obtained by the design method comprises a combustion chamber wall surface, a cavity front edge wall surface, a cavity bottom wall surface, a first compression section wall surface, a second compression section wall surface, a first expansion section wall surface and a second expansion section wall surface; the molded line of the wall surface of the first compression section and the molded line of the wall surface of the second expansion section are spline curves, and the molded line of the wall surface of the second compression section and the molded line of the wall surface of the first expansion section are arc lines with equal radius; the bottom wall surface of the concave cavity, the wall surfaces of the first compression section and the second compression section, the wall surfaces of the first expansion section and the wall surfaces of the second expansion section are smoothly connected. The engine combustion chamber and the spray pipe in the thrust chamber are in continuous transition and are integrally designed, so that the depth matching of the parameters of the combustion chamber and the inlet of the spray pipe is realized, and the thrust performance of the spray pipe is effectively improved; the thrust distribution of the thrust chamber component is effectively optimized, shock waves are eliminated, internal flow loss is reduced, and the performance of the engine is improved.

Description

Low-resistance and high-efficiency scramjet engine thrust chamber integrated design method
Technical Field
The invention relates to the technical field of engines, in particular to a low-resistance and high-efficiency scramjet engine thrust chamber integrated design method.
Background
The hypersonic aircraft is a strategic high technology for realizing high-speed penetration, global arrival within 2 hours and low-cost space entry, the development of the hypersonic aircraft changes the future war form, the hypersonic aircraft is a new high-point of aerospace technology in the 21 st century, and the countries in the world compete to develop related technologies and form a new threat to the national security of China. The scramjet engine is used as the best alternative power device for hypersonic air-breathing flight, and has become a hot point of research in various aerospace countries. As a core component of the scramjet engine, the performance of the supersonic combustor directly determines the success or failure of the whole engine development. Due to the high incoming flow speed and the short residence time, the scramjet engine usually adopts a concave cavity structure to stabilize flame and organize combustion. The high-temperature fuel gas generated by combustion in the combustion chamber is expanded and accelerated through the spray pipe to form thrust.
In the existing scramjet engine design, a combustion chamber and a spray pipe are separately and sectionally designed, so that the problem of mismatching of flow parameters exists, and the combustion efficiency and the thrust efficiency of the engine are not improved; the cavity placed in the supersonic airflow is an important part for internal resistance and thrust loss of an engine, a high-pressure combustion area in the cavity directly forms acting force opposite to the propelling direction on the wall surface of the rear edge, and negative thrust formed on the wall surface of the rear edge is a main source of resistance of a combustion chamber.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides the low-resistance and high-efficiency scramjet engine thrust chamber integrated design method, through the integrated design, the engine combustion chamber and the jet pipe are in continuous transition, the deep matching of the inlet parameters of the combustion chamber and the jet pipe is realized, and the thrust performance of the jet pipe is effectively improved.
In order to achieve the purpose, the invention provides a low-resistance and high-efficiency scramjet engine thrust chamber, which comprises a combustion chamber wall surface, a cavity front edge wall surface, a cavity bottom wall surface, a first compression section wall surface, a second compression section wall surface, a first expansion section wall surface and a second expansion section wall surface which are sequentially connected along the incoming flow direction of an engine;
the molded line of the wall surface of the first compression section and the molded line of the wall surface of the second expansion section are spline curves, and the molded line of the wall surface of the second compression section and the molded line of the wall surface of the first expansion section are arc lines with equal radius;
and the bottom wall surface of the concave cavity is smoothly connected with the wall surface of the first compression section, the wall surface of the first compression section is smoothly connected with the wall surface of the second compression section, the wall surface of the second compression section is smoothly connected with the wall surface of the first expansion section, and the wall surface of the first expansion section is smoothly connected with the wall surface of the second expansion section.
As a further improvement of the above technical solution, the profile of the first compression section wall surface is a second-order continuously-conductive spline curve, the first derivative and the second derivative of one end of the profile of the first compression section wall surface are equal to the first derivative and the second derivative of the corresponding end of the cavity bottom wall surface, and the first derivative and the second derivative of the other end of the profile of the first compression section wall surface are equal to the first derivative and the second derivative of the corresponding end of the second compression section wall surface.
As a further improvement of the above technical solution, the molded line of the cavity front edge wall surface and the molded line of the cavity bottom wall surface are both straight lines, the molded line of the cavity bottom wall surface is parallel to the molded line of the combustion chamber wall surface, and the molded line of the cavity front edge wall surface, the molded line of the cavity bottom wall surface and the molded line of the combustion chamber wall surface are both vertically connected.
In order to achieve the purpose, the invention also provides an integrated design method of the low-resistance and high-efficiency scramjet engine thrust chamber, which comprises the following steps:
step 1, giving the depth of the front edge wall surface of the concave cavity and the axial total length of the concave cavity, wherein the axial total length of the concave cavity is the sum of the axial lengths of the bottom wall surface of the concave cavity, the wall surface of the first compression section and the wall surface of the second compression section;
step 2, carrying out numerical simulation on the basis of air parameters in the engine inflow direction, the size of an inlet of a combustion chamber, the depth of the front edge wall surface of the concave cavity and the axial total length of the concave cavity, obtaining the length of a backflow area in the concave cavity on the basis of the numerical simulation result, namely obtaining the axial length of the bottom wall surface of the concave cavity, and obtaining the axial length sum of the wall surface of the first compression section and the wall surface of the second compression section on the basis of the axial total length of the concave cavity and the axial length of the bottom wall surface of the concave cavity;
step 3, obtaining the throat height of the thrust chamber based on the air parameters of the engine in the incoming flow direction, wherein the throat is the joint between the wall surface of the second compression section and the wall surface of the first expansion section;
step 4, selecting a second-order continuously-conductive spline curve as a molded line of the first compression section wall surface, selecting a circular arc line as a molded line of the second compression wall surface, obtaining the molded line radius of the second compression wall surface based on the throat height, and obtaining the axial lengths of the first compression section wall surface and the second compression section wall surface and the curve configuration of the molded line of the first compression section wall surface by combining the deflection angle of the second compression wall surface;
step 5, obtaining the axial total length of a thrust chamber based on structural constraint of engine design, and obtaining the axial total length of an expansion section based on the axial total length of the thrust chamber, the axial length of a first compression section wall surface and the axial length of a second compression section wall surface, wherein the axial total length of the thrust chamber is the sum of the axial lengths of a first compression section wall surface, a second compression section wall surface, a first expansion section wall surface and a second expansion section wall surface, the axial total length of the expansion section is the sum of the axial lengths of the first expansion section wall surface and the second expansion section wall surface, a molded line of the first expansion section wall surface is an arc line, the radius of the molded line of the first expansion section wall surface is equal to the radius of a molded line of the second compression section wall surface, and the axial length of the first expansion section wall surface is equal to the axial length of the second compression section wall surface;
and 6, obtaining the axial length and the profile configuration of the wall surface of the second expansion section based on the throat flow parameters, the axial total length of the expansion section, the throat height and the outlet size constraint of the thrust chamber.
As a further improvement of the above technical solution, in step 3, the obtaining of the throat height of the thrust chamber based on the air parameter in the engine inflow direction specifically includes:
Figure BDA0002818695800000031
in the formula, h8The throat height of the thrust chamber;
Figure BDA0002818695800000032
is the engine flow, T0Is the total temperature, P, of the combustion chamber0Mach number is designed for the pressure of the combustion chamber, M is the throat part of the thrust chamber, R is a gas constant, and gamma is a specific heat ratio.
As a further improvement of the above technical solution, in step 4, the axial lengths of the first compression section wall surface and the second compression section wall surface and the curve configuration of the molded line of the first compression section wall surface are obtained by combining the deflection angle of the second compression section wall surface, which specifically includes:
the molded line of the second compression wall surface is a circular arc line with the radius of R5The deflection angle is theta, and the end of the circular arc lineThe position is the throat part of the thrust chamber, and the coordinate of one end point of the molded line of the second compression wall surface is obtained because the throat part height is obtained in the step 3;
radius of bonding R5The deflection angle theta can obtain all coordinates of the molded line of the second compression wall surface, and the coordinate position of an end point on the molded line of the first compression section wall surface can be further obtained due to the fact that the molded line of the second compression wall surface is intersected with the molded line of the first compression wall surface;
meanwhile, the depth of the cavity front edge wall surface and the axial length of the cavity bottom wall surface are obtained in the step 1 and the step 2, so that all coordinates of the molded line of the cavity bottom wall surface can be obtained, and the molded line of the cavity bottom wall surface is intersected with the molded line of the first compression wall surface, so that the coordinate position of the other end point on the molded line of the first compression section wall surface is obtained;
on the premise that coordinates of two end points of a molded line of the wall surface of the first compression section are known and the molded line is a second-order continuously-derivable spline curve, the coordinates of all points on the molded line of the wall surface of the first compression section can be determined; the axial length l of the wall surface of the first compression section and the wall surface of the second compression section can be obtained5、l6And a profile of the first compression stage wall.
In order to achieve the purpose, the invention also provides a scramjet engine which is provided with the low-resistance and high-efficiency scramjet engine thrust chamber.
The low-resistance and high-efficiency scramjet engine thrust chamber integrated design method provided by the invention has the following beneficial effects:
1. the engine combustion chamber and the spray pipe are in continuous transition and are integrally designed, so that the depth matching of the parameters of the combustion chamber and the spray pipe inlet is realized, and the thrust performance of the spray pipe is effectively improved;
2. the thrust distribution of the thrust chamber component is effectively optimized, shock waves are eliminated, internal flow loss is reduced, and the performance of the engine is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic diagram of a thrust chamber of the prior art;
FIG. 2 is a schematic structural diagram of a thrust chamber of a low-resistance and high-efficiency scramjet engine in an embodiment of the invention;
FIG. 3 is a schematic flow chart of a low-resistance and high-efficiency scramjet engine thrust chamber integrated design method in the embodiment of the invention;
FIG. 4 is a size schematic diagram in the process of the integrated design method of the thrust chamber of the low-resistance and high-efficiency scramjet engine in the embodiment of the invention.
The reference numbers indicate: the combustion chamber comprises a combustion chamber wall surface 1, a cavity front edge wall surface 2, a cavity bottom wall surface 3, a first compression section wall surface 4, a second compression section wall surface 5, a first expansion section wall surface 6 and a second expansion section wall surface 7.
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise explicitly stated or limited, the terms "connected", "fixed", and the like are to be understood broadly, for example, "fixed" may be fixedly connected, may be detachably connected, or may be integrated; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
Fig. 2 shows that the low-resistance and high-efficiency scramjet engine thrust chamber disclosed in the present embodiment includes a combustion chamber wall surface 1, a cavity front edge wall surface 2, a cavity bottom wall surface 3, a first compression section wall surface 4, a second compression section wall surface 5, a first expansion section wall surface 6, and a second expansion section wall surface 7, which are sequentially connected in the engine inflow direction; the molded line of the first compression section wall surface 4 and the molded line of the second expansion section wall surface 7 are spline curves, and the molded line of the second compression section wall surface 5 and the molded line of the first expansion section wall surface 6 are arc lines with equal radius; the wall surface 3 of the bottom of the concave cavity is smoothly connected with the wall surface 4 of the first compression section, the wall surface 4 of the first compression section is smoothly connected with the wall surface 5 of the second compression section, the wall surface 5 of the second compression section is smoothly connected with the wall surface 6 of the first expansion section, and the wall surface 6 of the first expansion section is smoothly connected with the wall surface 7 of the second expansion section.
Preferably, the profile of the first compression section wall surface 4 is a second-order continuously-conductive spline curve, the first derivative and the second derivative of one end of the profile of the first compression section wall surface 4 are equal to the first derivative and the second derivative of the corresponding end of the cavity bottom wall surface 3, and the first derivative and the second derivative of the other end of the profile of the first compression section wall surface 4 are equal to the first derivative and the second derivative of the corresponding end of the second compression section wall surface 5.
It should be noted that in the present embodiment, the profile of the cavity leading edge wall surface 2 and the profile of the cavity bottom wall surface 3 are both straight lines, the profile of the cavity bottom wall surface 3 is parallel to the profile of the combustion chamber wall surface 1, and the profile of the cavity leading edge wall surface 2 is vertically connected with the profile of the cavity bottom wall surface 3 and the profile of the combustion chamber wall surface 1.
Based on the structure of the low-resistance and high-efficiency scramjet engine thrust chamber, the embodiment also discloses a low-resistance and high-efficiency scramjet engine thrust chamber integrated design method, and referring to fig. 3-4, the design method specifically comprises the following steps:
step 1, the depth of the front edge wall surface of the cavity and the axial total length L of the cavity are given1(ii) a Wherein the axial total length of the concave cavity is the axial length l of the bottom wall surface of the concave cavity3Axial length l of wall surface of first compression section4And the axial length l of the wall surface of the second compression section5Length of (a) and, namely L1＝l3+l4+l5；
Step 2, carrying out numerical simulation based on air parameters of the engine in the inflow direction, the size of an inlet of the combustion chamber, the depth of the front edge wall surface of the concave cavity and the axial total length of the concave cavity, and obtaining the length of a backflow area in the concave cavity based on the numerical simulation result, namely obtaining the axial length l of the bottom wall surface of the concave cavity3The axial length and the axial length l of the axial length of the wall surface of the first compression section and the wall surface of the second compression section can be obtained simultaneously by combining the step 14+l5Taking the value of (A);
and 3, obtaining the throat height of the thrust chamber based on the air parameters of the engine in the incoming flow direction, wherein the throat is the joint between the wall surface of the second compression section and the wall surface of the first expansion section, and specifically comprises the following steps:
Figure BDA0002818695800000061
in the formula, h8The throat height of the thrust chamber;
Figure BDA0002818695800000062
is the engine flow, T0Is the total temperature, P, of the combustion chamber0Mach number is designed for the pressure of the combustion chamber, M is the throat part of the thrust chamber, R is a gas constant, and gamma is a specific heat ratio;
step 4, selecting a second-order continuously-conductive spline curve as a molded line of a first compression section wall surface, selecting a circular arc line as a molded line of a second compression wall surface, obtaining a molded line radius R5 of the second compression wall surface based on the throat height, and passing through a given deflection angle theta of the second compression wall surface;
knowing that the molded line of the second compression wall surface is an arc line, the radius of the arc line is R5, the deflection angle is theta, and the tail end position of the arc line is the throat part of the thrust chamber, obtaining the coordinate of one end point of the molded line of the second compression wall surface as the throat part height is obtained in the step 3, and obtaining all coordinates of the molded line of the second compression wall surface by combining the radius R5 and the deflection angle theta, wherein the coordinate position of one end point on the molded line of the first compression section wall surface can be obtained as the molded line of the second compression wall surface is intersected with the molded line of the first compression wall surface; and meanwhile, the depth of the cavity front edge wall surface and the axial length of the cavity bottom wall surface are obtained in the step 1 and the step 2, so that all coordinates of the molded line of the cavity bottom wall surface can be obtained, and the molded line of the cavity bottom wall surface is intersected with the molded line of the first compression wall surface, so that the coordinate position of the other end point on the molded line of the first compression section wall surface is obtained. Coordinates of two end points of a molded line of the wall surface of the known first compression section and a spline curve of which the molded line is continuously guided in a second order can be determined, namely the coordinates of all points on the molded line of the wall surface of the first compression section; the axial length l of the wall surface of the first compression section and the wall surface of the second compression section can be obtained5、l6And the shape of the wall of the first compression stageThe curved configuration of the line.
And 5, obtaining the axial total length of the thrust chamber based on structural constraint of engine design, and obtaining the axial total length of the expansion section based on the axial total length of the thrust chamber, the axial length of the wall surface of the first compression section and the axial length of the wall surface of the second compression section, wherein the axial total length L of the thrust chamber2Is the axial length l of the wall surface of the first compression section4Axial length l of the wall of the second compression section5Axial length l of the first expansion section wall surface6Axial length l of the wall of the second expansion section7Length of (a) and, namely L2＝l4+l5+l6+l7(ii) a The total axial length of the expansion section is the axial length l of the wall surface of the first expansion section6Axial length l of the wall of the second expansion section7The molded line of the first expansion section wall surface is a circular arc line and the radius R thereof6The axial length of the first expansion section wall surface is equal to the axial length of the second compression section wall surface, namely R5＝R6，l5＝l6；
Step 6, based on the flow parameters of the throat part and the axial total length L of the expansion section3＝l6+l7Height of throat h8Constrained h with the size of the outlet of the thrust chamber7And obtaining the axial length and the profile configuration of the wall surface of the second expansion section. The throat flow parameters comprise throat temperature and throat pressure, and specifically comprise:
Figure BDA0002818695800000071
Figure BDA0002818695800000072
wherein T is the throat temperature and p is the throat pressure.
In this embodiment, the Rao method of the maximum thrust nozzle design is adopted to obtain the axial length and the profile configuration of the wall surface of the second expansion section, so as to complete the matching design of the profile of the expansion section. The specific process may be referred to in Maurice J.Zurow, Joe D.Hoffman, Gas Dynamics Volume II,1977, John Wiley & Sons, p164-169 ", which is not repeated herein.
Based on the low-resistance and high-efficiency scramjet engine thrust chamber integrated design method, the low-resistance and high-efficiency scramjet engine thrust chamber in the embodiment can be obtained, the engine combustion chamber and the jet pipe in the thrust chamber are in continuous transition, and the integrated design is adopted, so that the depth matching of the parameters of the combustion chamber and the inlet of the jet pipe is realized, and the thrust performance of the jet pipe is effectively improved; meanwhile, the thrust distribution of the thrust chamber component can be effectively optimized, shock waves are eliminated, internal flow loss is reduced, and the performance of the engine is improved.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.

Claims (3)

1. The low-resistance and high-efficiency scramjet engine thrust chamber comprises a combustion chamber wall surface, a concave cavity front edge wall surface, a concave cavity bottom wall surface, a first compression section wall surface, a second compression section wall surface, a first expansion section wall surface and a second expansion section wall surface which are sequentially connected along the engine inflow direction;
the molded line of the wall surface of the first compression section and the molded line of the wall surface of the second expansion section are spline curves, and the molded line of the wall surface of the second compression section and the molded line of the wall surface of the first expansion section are arc lines with equal radius;
the bottom wall surface of the concave cavity is smoothly connected with the wall surface of the first compression section, the wall surface of the first compression section is smoothly connected with the wall surface of the second compression section, the wall surface of the second compression section is smoothly connected with the wall surface of the first expansion section, and the wall surface of the first expansion section is smoothly connected with the wall surface of the second expansion section;
the molded line of the first compression section wall surface is a second-order continuously-conductive spline curve, the first derivative and the second derivative of one end of the molded line of the first compression section wall surface are equal to those of the corresponding end of the cavity bottom wall surface, and the first derivative and the second derivative of the other end of the molded line of the first compression section wall surface are equal to those of the corresponding end of the second compression section wall surface;
the molded line of the concave cavity front edge wall surface and the molded line of the concave cavity bottom wall surface are both straight lines, the molded line of the concave cavity bottom wall surface is parallel to the molded line of the combustion chamber wall surface, and the molded line of the concave cavity front edge wall surface, the molded line of the concave cavity bottom wall surface and the molded line of the combustion chamber wall surface are vertically connected;
the design method is characterized by comprising the following steps:
step 1, giving the depth of the front edge wall surface of the concave cavity and the axial total length of the concave cavity, wherein the axial total length of the concave cavity is the sum of the axial lengths of the bottom wall surface of the concave cavity, the wall surface of the first compression section and the wall surface of the second compression section;
step 2, carrying out numerical simulation on the basis of air parameters in the engine inflow direction, the size of an inlet of a combustion chamber, the depth of the front edge wall surface of the concave cavity and the axial total length of the concave cavity, obtaining the length of a backflow area in the concave cavity on the basis of the numerical simulation result, namely obtaining the axial length of the bottom wall surface of the concave cavity, and obtaining the axial length sum of the wall surface of the first compression section and the wall surface of the second compression section on the basis of the axial total length of the concave cavity and the axial length of the bottom wall surface of the concave cavity;
step 3, obtaining the throat height of the thrust chamber based on the air parameters of the engine in the incoming flow direction, wherein the throat is the joint between the wall surface of the second compression section and the wall surface of the first expansion section;
step 4, selecting a second-order continuously-conductive spline curve as a molded line of the first compression section wall surface, selecting a circular arc line as a molded line of the second compression wall surface, obtaining the molded line radius of the second compression wall surface based on the throat height, and obtaining the axial lengths of the first compression section wall surface and the second compression section wall surface and the curve configuration of the molded line of the first compression section wall surface by combining the deflection angle of the second compression wall surface;
step 5, obtaining the axial total length of a thrust chamber based on structural constraint of engine design, and obtaining the axial total length of an expansion section based on the axial total length of the thrust chamber, the axial length of a first compression section wall surface and the axial length of a second compression section wall surface, wherein the axial total length of the thrust chamber is the sum of the axial lengths of a first compression section wall surface, a second compression section wall surface, a first expansion section wall surface and a second expansion section wall surface, the axial total length of the expansion section is the sum of the axial lengths of the first expansion section wall surface and the second expansion section wall surface, a molded line of the first expansion section wall surface is an arc line, the radius of the molded line of the first expansion section wall surface is equal to the radius of a molded line of the second compression section wall surface, and the axial length of the first expansion section wall surface is equal to the axial length of the second compression section wall surface;
step 6, based on the throat flow parameters, constraining the axial total length, the throat height and the outlet size of the thrust chamber of the expansion section to obtain the axial length and the profile configuration of the wall surface of the second expansion section;
in step 3, the obtaining of the throat height of the thrust chamber based on the air parameter of the engine in the incoming flow direction specifically comprises:
Figure 226559DEST_PATH_IMAGE002
in the formula (I), the compound is shown in the specification,
Figure 612541DEST_PATH_IMAGE004
the throat height of the thrust chamber;
Figure 861120DEST_PATH_IMAGE006
is the flow rate of the engine,T 0Is the total temperature of the combustion chamber,P 0Mach number designed for combustion chamber pressure and M for thrust chamber throat,RIs a gas constant,
Figure 725170DEST_PATH_IMAGE008
Is the specific heat ratio;
in step 6, the throat flow parameters include throat temperature and throat pressure, and specifically include:
Figure 8384DEST_PATH_IMAGE010
in the formula (I), the compound is shown in the specification,Tis the temperature of the throat part of the body,pis the pressure of the throat part of the patient,T 0is the total temperature of the combustion chamber,P 0Is the combustion chamber pressure.
2. The low-resistance and high-efficiency scramjet engine thrust chamber integrated design method of claim 1, wherein in the step 4, the axial lengths of the first compression section wall surface and the second compression section wall surface and the curve configuration of the molded line of the first compression section wall surface are obtained by combining a deflection angle of the second compression wall surface, and the specific steps are as follows:
the molded line of the second compression wall surface is a circular arc line with the radius of R5The deflection angle isθMeanwhile, the tail end position of the arc line is the throat part of the thrust chamber, and the coordinate of one end point of the molded line of the second compression wall surface is obtained because the throat part height is obtained in the step 3;
radius of bonding R5Angle of deflectionθAll coordinates of the molded line of the second compression wall surface can be obtained, and the coordinate position of an end point on the molded line of the first compression section wall surface can be obtained due to the fact that the molded line of the second compression wall surface is intersected with the molded line of the first compression wall surface;
meanwhile, the depth of the cavity front edge wall surface and the axial length of the cavity bottom wall surface are obtained in the step 1 and the step 2, so that all coordinates of the molded line of the cavity bottom wall surface can be obtained, and the molded line of the cavity bottom wall surface is intersected with the molded line of the first compression wall surface, so that the coordinate position of the other end point on the molded line of the first compression section wall surface is obtained;
on the premise that coordinates of two end points of a molded line of the wall surface of the first compression section are known and the molded line is a second-order continuously-derivable spline curve, the coordinates of all points on the molded line of the wall surface of the first compression section can be determined; the axial length l of the wall surface of the first compression section and the wall surface of the second compression section can be obtained5、l6And a profile of the first compression stage wall.
3. A scramjet engine characterized by having a low resistance and high efficiency scramjet thrust chamber designed by the design method of claim 1 or 2.
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